Rocket projector



4 Sheets-Sheet l Apnl 18, 1950 L. A. SKINNER Er AL ROCKET PROJECTOR Filed Oct. 3, 1944 v m a WMM ill April 18, 1950 L. A. SKINNER ET AL 2,504,160

ROCKET PROJECTOR Filed Oct. 3, v1944 4 Sheets-Sheet 2 o mllllj R llllllllf l a/ A5- ROCKET PROJECTOR Filed 001:. 3, 1944 4 Sheets-Sheet 3 gmwwtom R E N aw m \m mm A 1 s w a w E u M. mum LJ mm DN Rm c: eW-d A ril 18, 1950 L. A. SKINNER ET AL 2,504,160

ROCKET PROJECTOR 7 Filed Oct. 3, 1944 '4 Sheets-Sheet 4 Patented Apr. 18, 1950 UNITED STATES PATENT OFFICE ROCKET PROJECTOR Leslie A. Skinner, Berkeley, Calif., and

Julius A. Folse, Miami, Fla.

Application October 3, 1944, Serial N ,557,04c

(crass-1.7.)

(Granted under the act of March 3, 1883, as

4 Claims.

The invention described herein maybe manufactured and used by or for the Government for governmental purposes without the payment to us of any royaltythereon.

This invention relates to a rocket projector, more particularly to a gas deflector for mounted rocket projectors.

ment as shown in the accompanying drawings in which:

Fig. l is a side elevational viewof therocket projector shown supportedon atripod. mount.

Fig. 2 is a plan view of the rocket projector.

Fig. 3 is an enlarged cross sectional .view .taken along the plane 3-3 of Fig. 1.

Fig. 4 is an enlarged fragmentary longitudinal sectional view taken along the plane, 4-4. of Fig. 3.

Fig. 5 isan enlarged fragmentary side elevational view of the loading gate.

Fig. 6 is a cross sectional .view taken along the plane 66 of Fig. 5.

Fig. 7 is an enlarged detail .view taken along the plane l--l of Fig. 5.

Fig. 8 is an enlarged detail fragmentaryview showing the percussion firing mechanism in relation to a rocket projectile positioned within the rocket projector.

Fig. 9 is an enlarged detail view of. the percussion firing mechanism shown in Fig. 8.

This invention essentially comprises a long projector tube pivotally mounted in a yoke which is rotatably mounted in a tripod. Each-endIof the projector tube is open and one end ofsaid -rtube is pivotally connected to alargehorizontal'defiector. An elevating mechanism is mounted: on top of the deflector and connection-is made to the projector tube to elevate or depress such tube. The projector tube is readily traversed in azimuth by a crank thru a gear train connecting thernovable yoke with a stationary tripod. A loading gate is provided on the projector tube toiacilitate loading a rocket projectile intosuch tube.

There is shown in assembled relationin Fig.,;-1 arocket projector embodying this invention. cylindrical tube l is provided to direct the inithe semi-cylindrical portion 6.

amended. April 30, 1928.; 370 0. G. 757) .tial flight of a rocket projectile 2 shown in dotted outline in Fig. 1. Tube is preferably of such length as to permitcomplete burning of the rocket propellent of rocket projectile 2 before such projectile leaves tube I. A pair of brackets .3 are secured to the rear end of tube l preferably by welding as shown in Figs. 1 and 2. Brackets 3 vare oppositely disposed and form a U-shape as .shown in top elevation in Fig. 2. A stiffening web 4 is welded to each bracket 3 as shown in -Fig. 2.

Tube lis pivotally mounted on a yoke 5. The yoke 5 comprises asemi-cylindrical portionli and a stem M vertically secured to the underside of A boss 1 is secured as by weldinglio the upper portion of each side of vyoke 5 to provide a suitable bearing surface betweeneach bracket 3 and yoke 5. Ahorizontal pin 8 is suitably secured in each bQSs-l projecting outwardly from yoke 5 to pivotally engage each bracket 3 on said yoke. Thus tube I is pivotallysecured to yoke 5 about a horizontal axis.

Stem portion of yoke5 is vertically mounted in a hub .9 or .atripod ,mount m. Tripod mount ,lll comprises the hub 9 and three radiallyextending legs ll, l2, and i3 equally disposed around hub 9. Such legs are preferably securedtohubfl by .welding. The lower end of stem portion l-.4

.is ofreduced diameter and is provided with thread 15. Awasher l6 surrounds stem portion [4 adjacent the bottom of hub 9. A pair of nuts I! are screwed ontoi thread l5 of stem portion l4 pivotally securing the yoke .5 totripod mount l0 on a vertical axis. A boss [.8 is secured to the outer end of,legs H, l2, and I3 preferably by a. bolt L9. .A vertically threaded holeZfl is provided in each boss 18in which is screwed a threaded elevating rod 2i. -A crank 22 is provided preferably integrally formed on the upper end of each rod 2|. .The lower end of each elevating rod 21 is secured to ,a suitable foot 24 as by .a ball and socket joint 23.

1T0 traverse tube 1 a traversing mechanism 25 .as ;shown in Flgs. l and 3 is provided. ,Such mechanism essentially (comprises a crank 25, a spur gear 21, and a ring gear 28. Ring gear;28

surrounds stern portion l4 and ,is fixedly secured to top ofhub 9. Anannular housin 29 surro ri se r h h necomprisinea -.ring portion 30 having an integral vertical flange -31. The ring ,portionBD is secured to top of .hub ,9,;as1by'bolts;,,32. A cover 33 is placed over flanged -ring-;30, .which is ghCld thereon by stem portion I4 of yoke 5.

-mounted on top of deflector 48.

A shaft 34 is vertically supported near the outside edge of rin gear 28 in a bracket 35. Bracket 35 is preferably secured to stem portion I4 of yoke 5 by welding. The shaft 34 passes thru an integral boss 36 provided on the top of cover 33. The spur gear 21 is suitably secured to the lower end of shaft 34 and engages ring gear 28. Crank 26 is obliquely mounted to the upper portion of semi-cylindrical member 6 of yoke 5 by a bracket 31. Such bracket is secured to the member 6 as by a bolt 38. Connection is made between vertical shaft 34 and crank 26 by a conventional universal joint 39. By turning crank 26 spur gear 21 revolves about the periphery of ring gear 28 and thru the connection of shaft 34 to stem I4 by bracket 35, yoke 5 and hence tube I are rtated to permit adjustment in azimuth for sighting purposes. I

A deflector 48 is mounted within the semicylindrical member 6 of yoke 5. The deflector 46 is a tubular member of substantially larger diameter than that of tube I and such deflector is preferably welded to the inside of the member 6. The rear end of deflector 48 is flared outwardly as shown at 4| in Figs. 1 and 2. The forward end of deflector 48 is slotted as shown at 42 to permit tube to enter the forward end of such deflector. The forward end of deflector 48 is arcuately formed as shown in Fig. 1 to perrnit tube I to be raised from a horizontal position to a nearly vertical position as shown in such figure in dotted outline. The rocket gases are therefore always discharged parallel to the ground and at the same vertical level regardless of the elevational position of the projector tube I.

To raise tube I an elevating mechanism is The elevating mechanism essentially comprises a threaded elevating shaft 43 mounted within a housing 44, shaft 43 arranged to be rotated by a crank 45 thru a gearing connection to such shaft. Housing 44 is of substantially rectangular shape and is pivotally mounted within a U-shaped bracket 46 (Fig. 3). Bracket 46 is mounted on top of deflector 48 and is secured thereto preferably by welding. On opposite sides of housing 44 there are suitably'secured thereto horizontal pins 41.

Pins 41 are constructed to be in suitable recesses on top of bracket 46. A semi-circular clamp 48 is then placed over each of pins 41 and such clamp is secured to bracket 46 as by bolts '49} Thus housing 44 is pivotally secured to bracket operating with bevel gear 52 lies within housing 44 and is keyed to the crank 45 which passes thru an integral boss 56 provided on the side of housing 44. The forward end of threaded shaft 43 is pivotally secured to a bifurcated lug 57 provided on top of tube I.

A helical tension spring 58 surrounds threaded shaft 43 and is secured between lug 57 and the forward face of housin 44. Spring 58 is provided to facilitate raising tube I.

Spring 58 is suitably secured to housing 44 and lug so that such spring will exert a tension force at all times. Thus it may be readily seen that by turning crank 45, threaded shaft 43 can be readily screwed in and out of housing 44 thru the connection of gears 55 and 52 to raise or lower tube I to any elevation desired within the limit of travel as shown in dotted outline in Fig. 1. A flexible cover 5 including an expander spring 59 may be provided to enclose shaft 43 between housing 44 and lug 51.

To facilitate insertion of the rocket projectile 2 into tube I in proper relationship to the firing mechanism to be described, a loading gate 68 is provided. An opening comprising substantially one-half of the circumference of tube I and of a length to accommodate the rocket projectile 2 is provided in tube I. Such opening is closed by a cover 6| comprising inner and outer members 62 and 63 respectively of substantially semicylindrical construction. The inner member 62 is of the same arcuate configuration as tube I and snugly fits the opening above mentioned. The member 63 surrounding the outer periphery of such inner member overlaps each side of the inner member 62 as shown in Fig. 6. A plurality of straps 64 surround the outer periphery of cover 6| and are preferably evenly spaced along the length thereof as shown in Figs 1 and 2. Each strap 64 is secured to cover 6| by bolts 65 as shown in Fig. 6. The left end of each strap 64 as shown in Fig. 6 is provided with a hinge joint 66. A plurality of straps 6! similar to straps 64 are secured to the underside of tube I as by bolts 68. The left end of such straps is hinged to the upper strap 64 as by a pin 69. A plurality of lugs I8 shaped as shown in Fig. 6 are provided on the hinged edge of cover 6| to limit the extent that cover 6| can be raised.

The cover 6| is locked to tube I by a plurality of links II. The links II are hinged by pins 8| to bifurcated lugs I2 which are suitably secured to straps 64 as by Welding. The other ends of links 1| are pivotally mounted to a locking bar I4, such links being mounted on longitudinal pins I5 which pass thru a plurality of integral lugs I6 on bar I4 located opposite each link 7|. An integral longitudinal shoulder 14a is provided on the underside of bar I4. A plurality of adjusting screws I9 are equally disposed along the length of shoulder 14a and such screws bear against a locking bar I8. Locking bar I8 is secured to the underside of bar I4 by a plurality of equally disposed screws lI. Screws 17 pass thru slotted holes in bar I4 and engage suitably threaded holes in looking bar I8. The slotted holes in bar 14 permit circumferential adjustment of locking bar I8. The forward edge of locking bar I8 is sloped as shown in Fig. 6. A handle 82 is secured to the center of bar I4 as shown in Figs. 5 and 6 to facilitate raising cover 6|. With handle 82 in the lowered or locked position as shown in Fig. 6, the sloped forward edge of looking bar I8 cooperates with a corresponding sloped edge on a locking bar 18a longitudinally secured to each strap 6I as by welding. In the locked position shown in Fig. 6 locking bar 78 is readily adjusted to insure that cover 6| will be maintained in the closed position while firing a rocket projectile in the projector. Such adjustment is made by unloosening screws 71 and tightening screws I9 until the sloped forward edge of locking bar I8 snugly engages the corresponding sloped surface on the corresponding locking member 18a. When properly adjusted, screws 11 are firmly tightened to secure lockin bar 18 in the proper position. The cover 6| is then readily unlocked by raising handle 82. Such unlocking is readily effected because the point .of engagement of the locking bar .13 and thelocking member 180. lies'outside of a line between the centers of pins .15 andlfil. Straps 64 are loosely secured to cover M by virtue of slotted holes in straps 64 thru which bolts 65 are inserted. It is this looseness of fit which permits a better engagement of cover 6| and facilitates locking such cover in the locked position. An integral lug 30 is .pro'videdon :the upper end of links H to limit the rotational movement of links H about pins Bl. v

To load a rocket projectileintoltube I, handle 82 is raised upwardly or in a counterclockwise direction as shown in Fig. 6. Unlocking is readily effected as the engagementof locking bar 78 with looking member 18a is not on the same line as the centers of pins T5 and 8|, hence bar 14 and locking bar Hlis rotated out of engagement with looking member 18a by links H. When lug 80 on each link 1| strikes eachstrap 64 rotational movement is then imparted to cover 81 thereby opening such cover. When lug l strikes the side of tube I further movement of cover is arrested. Such lug also servesto hold cover BE in the open position for convenience in loading a projectile into tube I. The fullyopen-position of such cover is shown in dotted outline in Fig. 6.

The type of firing mechanism utilized with this rocket projectile is a percussion type of mechanism and such mechanism is shown in detail in Figs. 8 and 9. The mechanism shown in such figure comprises essentially a hammer 83, a sear 84, and a sear release member 85. This mechanism is contained within a horizontal housing 86 of substantially rectangular configuration which is secured to the underside of tube l as by welding. Hammer 83 is pivotally mounted on transverse pin 81. In the cooked position hammer 83 lies horizontally along the underside of tube I. A suitable opening is provided in the underside of tube l to permit hammer 83 to be biased upwardly into tube l to strike a primer 88 of rocket projectile 2. An integral lug 89 is provided on hammer 83 opposite pin 81 as shown in Fig. 8.

A spring 90 disposed horizontally within housing 86 is secured to lug B9 and to the rear end of housing 86 and such spring provides the bias to hammer 83 to effect discharge of rocket projectile 2.

The sear 84 is horizontally mounted between two downwardly projecting brackets 9| and 92. The brackets 9| and 92 are secured to the top of housing 86 and preferably by welding. The rear end 93 of sear 84 en ages a sear notch 94 provided in the pivoted end of hammer 83. A helical spring 95 is placed about sear 84 and engages a split washer Ill) secured to sear 84 so as to bias the sear 84 rearwardly into engagement with sear notch 94 of hammer 83. An integral downwardly projecting lug 96 is provided. on the forward end of sear 84 which is engaged by a disconnector member 91. The disconnector member 9'! is pivotally mounted on a horizontal sear release member 98 by a pin 99. Disconnector 91 rests upon a sloped upper surface IUI of a stud IUD.

Sear release member 98 is horizontally mounted between two spaced brackets I02 preferably welded to the bottom of housing 36. A helical spring H33 surrounds member 98 and works between the forward bracket !!!2 and a split washer Ill connected to member 98 so as to bias the member 98 rearwardly. A spring I04 is suitably secured to disconnector 91 and to release member 6 98 to bias disconnector 91 upwardly. A lanyard 405 is suitably secured to the forwardend of sea! release member 98. Such lanyard passes over a pulley [I16 which is provided to reduce friction where lanyard I05 emerges thru a suitable hole in the forward end of housingfifi.

With hammer 83 L-in .the horizontal or cooked position as .shownin Fig. 8 release of :such ham-- mer is effected when lanyard I05 is pulled downwardly. This moves sear release member '98 and disconnector 9'. forwardly against the bias vof spring I03. Forward movement of disconnector 91 likewise produces a forward movement ofsear 84. Disconnector 91 is thus forced to ride upwardly along the sloped surface H of stud 1 00. This movement forces the forward :end of =disconnector Bl to drop off the lower end of lug 96 of sear 84. However justbefore disconnector 9-1 is droppedout of contact with the end offlug 96 of sear member 84,.the sloped end 53 of scar 84 becomes disengaged from sear-notch '94 on hammer 83. Thus hammer- 83 islbiased upwardly by spring whereby hammer'83 effects discharge of rocket projectile 2. When disconnector 91 slides off the end of lug $6 sear Sells-then forced rearwardly under the bias of spring tobear against the rounded 'endlof hammer 83 inpo'sition to engage sear notch 94 when hammer 83 is pivoted rearwardly about the pin 81 by the action of the gas blast. Upon release of lanyard 805 spring H33 biases member 98 rearwardly. Disconnector 9'! is then biased counterclockwise by spring )4 to again engage lug 96. If desired a cocking handle I07 as shown in Fig. 1 may be suitably mounted on the outside of housing 86 to manually lower hammer 83 to the cocked position shown in Fig. 8.

It is readily apparent from the foregoing description that a rocket projector capable of launching rocket projectiles of large caliber and one that is readily and conveniently sighted is hereby provided. The tripod on which this projector is mounted may be readily set up and adjusted even on rough terrain by individual adjustment of any one of feet 24 by means of crank 22. Adjustment for azimuth is quickly made by turning crank 26. Likewise elevation adjustment is conveniently obtained by rotation of crank 45 to elevate or depress tube l as may be desired. The proper elevation of tube I may be readily adjusted by use of a clinometer or by a suitable sight affixed to the projector. The gas blast resulting from discharge of rocket projectile 2 is discharged thru deflector 40 with a minimum of overturning force regardless of the elevation of tube l.

It is also apparent that the firing mechanism disclosed herein is of simple, rugged construction and is semi-automatic in action being cocked by the gas blast of the discharged projectile thereby leaving the operator free to devote his entire attention to loading and sighting the projector. It is further desired to point out that the rocket projector herein described may be readily mounted on a wheeled mount by mere substitution of such mount for tripod II].

We claim:

1. In a pivotally mounted rocket projector tube having open ends, a gas deflector mounted in cooperative relationship to the rear end of said projector tube, said gas deflector constructed and arranged to discharge rocket gases in substantially the same direction with respect to the ground independent of the elevation of said projector tube.

2. In a rocket projector tube, pivotal mounting means, a yoke, said yoke having a cylindrical stem cooperating with said pivotal mounting means, a gas deflector mounted on said yoke in cooperative relationship to the rear end of said projector tube, said gas deflector constructed and arranged to discharge the rocket gases in a plane .substantially parallel with the ground independent of the elevational position of said projector tube.

3. In a pivotally mounted rocket projector tube, a yoke, said yoke rotatably supporting a gas deflector, said gas deflector comprising a tubular member having an arcuately formed closed forward end slotted to receive the rear end of said projector tube for vertical movement therein and having its hear end opened and flared outwardly, :said gas deflector constructed and arranged to discharge the rocket gases in the same plane with respect to the ground independent of the elevation of said projector tube.

4. A gas deflector for a rocket projector, said gas deflector comprising a tubular member, one end of said tubular member arcuately formed and slotted to receive the discharge end of said 25 arranged to discharge rocket gas in a fixed plane regardless of the elevational position of said rocket projector.

LESLIE A. SKINNER. JULIUS A. FOLSE.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 16,070 Scharfie Nov. 11, 1856 932,270 Goodwin Aug. 24, 1909 1,395,630 Davis Nov. 1, 1921 1,500,711 Lafitte July 8, 1924 1,661,091 Riabouchinski Feb. 28, 1928 2,030,507 Driggs Feb. 11, 1936 FOREIGN PATENTS Number Country Date 25,326 Great Britain 1894 323,399 Germany July 22, 1920 464,543 Great Britain Apr. 20, 1937 OTHER REFERENCES Popular Science, July 1943, pp. 50-54, Rocket weapons, etc. 

